function GA_populationATKUpdate(population)
global conID
%% 根据种群修改卫星参数
% 获得星座中卫星数量
% 不使用全局变量
populationSize_temp = size(population,1);
populationNum_temp = size(population,3);
%population_end = GA_Decode(population);
population_end = population;
for i = 1:1:populationNum_temp
    for j = 1:1:populationSize_temp
        %%% 循环给定卫星动力学模型、坐标系及历元
        t = ['*/Satellite/Satellite',num2str(i),num2str(j),' Classical J2Numerical "26 Sep 2035 12:00:00.00" "28 Sep 2035 12:00:00.00" 60 j2000 "26 Sep 2035 12:00:00.00" '];
        %%% 给定卫星轨道根数
        a = num2str(population_end(j,1,i)*1e3);
        e = num2str(population_end(j,2,i));
        iAngle = num2str(population_end(j,3,i));RAAN = num2str(population_end(j,4,i));
        Perigee = num2str(population_end(j,5,i));meanAngle = num2str(population_end(j,6,i));
        space = ' ';
        %sat = t + a + space + e + space + iAngle + space + RAAN + space + Perigee + space + trueAngle;
        % SetState <VehObjectPath> Classical {Propagator} {NoProp | {TimeInter- val}} <StepSize> {CoordSystem} ...
        % "<OrbitEpoch>" <SemiMajorAxis> <Eccentricity> <Inclination> <ArgOfPerigee> <RAAN> <MeanAnom> ["<CoordEpoch>"]
        sat = [t,a,space,e,space,iAngle,space,Perigee,space,RAAN,space,meanAngle];
        %%% 根据给定参数设置各卫星状态
        atkConnect(conID, 'SetState', sat);
    end
end
end